GB556552A - Improvements in the mounting of aircraft flight controls - Google Patents

Abstract

556,552. Aircraft controls. GENERAL AIRCRAFT, Ltd., WELS, O., and MARCZEWSKI, Z. March 5, 1942, No. 2919. [Class 4] Bracket means attached to a strong point on the aircraft carries the elevator rudder and aileron controls which act through levers rotating with or on a common transverse shaft carried by the bracket means. In one form, two brackets 5, 6, connected by a fitting 7 to a cabin bulkhead, support two shafts 8, 23 carrying pillars 20, 22 on which a control member 21, 26, similar to that described in Specification 546,210, is mounted. An arm 10, Fig. 2, is fixed to the pillar 20 and is connected through a rod 12 and bell crank lever 29 to the elevator. An arm 27, fixed to the part 26 of the control member, is connected by a link 28 to a bell crank lever 11 pivoted on the shaft 8 and actuates the ailerons through a second rod 12 and bell crank lever 29. Two pedal levers 15, 16 are mounted on the shaft 8, the lever 16 being pinned thereto while the lever 51 is keyed to an arm 9 for actuating the rudder through a third rod 12 and bell crank lever 29. The two arms 15, 16 are constrained to move in opposite directions by links 19 and rocking lever 18. The setting of the control rods close together enables them to be grouped in a floor duct. The lower parts of the pedal levers are hinged to enable them to be adjusted to suit pilots of different leg lengths, a spigot 34, Fig. 4, movable by a treadle 38 engaging any of the three sockets shown. Fig. 5 shows another form in which all the controls are mounted on a tube 1 adapted to be secured to the airframe. In this case a control lever is mounted on a shaft 21 journalled in bearings suspended by links 20, 22 pivoted on transverse shafts 2, 3 extending from the tube 1. An arm 27 on the shaft 21 actuates the ailerons through a link 28 and lever 43, and an arm 44, keyed to the shaft 3 to which the link 22 also is keyed, actuates the elevator.' Two pedal levers 15, 16 respectively loose on and fixed to the shaft 2 are interconnected by a rocking-lever, not shown, and the lever 15 actuates the rudder through a link 4 and lever 42 pivoted on the shaft 3. In both forms dual controls may be coupled abreast by extending the shafts 8, 23 or 2, 3, the aileron controls being coupled by transverse rods extending from arms 27 on the rotating part of the column to the end of a lever mounted on a universal joint through which motion is transmitted to the aileron control. Alternatively two sets of controls may be mounted in tandem, the second set being connected to a second set of levers 29 in the transmission to the control surfaces. Specification 546,210 is referred to.